Q2 a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow direction(Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar anda temperature of 10°C. The top surface of the wing absorbs solar radiation at a rateof 800 W/m2. Assume the wing to be of solid construction and to have a single,uniform temperature. Estimate the steady-state temperature of the wing.Refer Table A-15 for air thermophysical properties.Aira conv9's,abs = 800 W/m²ĮU= 100 km/sToo=263 Kp= 0.7 bara convtamFigure 2- TsL = 2.5m TABLE A-15Properties of air at 1 atm pressureDynamicKinematicPrandtlTemp., Density,SpecificHeat,Cp. J/kg. °CThermalConductivity,k, W/m. °CThermalDiffusivity,a, m²/sViscosity,Number,T, °Cp. kg/m³Viscosity,v, m²/sμ, kg/m-sPr-1502.866983-100 2.0383.013 x 10-65.837 x 10-69660.011710.015820.019790.020570.72460.72630.7440-50 1.582-40 1.5149999.319 x 10-610021.008 x 10-50.743610040.02134-30 1.451-20 1.394-108.636 x 10-61.189 x 10-61.474 x 10-51.527 x 10-51.579 x 10-51.630 x 10-51.680 x 10-51.729 x 10-51.754 x 10-51.778 x 10-510050.022111.34110060.022881.087 x 10-51.169 x 10-51.252 x 10-51.338 x 10-51.382 x 10-50.74250.74080.73870.736210060.0236410060.0240110060.024391.426 x 10-51.470 x 10-50.024760 1.2925 1.26910 1.24615 1.22520 1.20425 1.18430 1.16435 1.14540 1.1271.802 x 10-50.73500.73360.73230.7309100710070.025141.516 x 10-51.825 x 10-51.849 x 10-51.562 x 10-50.025510.025881.872 x 10-510071007100710070.72960.72820.72680.72550.026250.026620.026991.608 x 10-51.655 x 10-51.702 x 10-51.750 x 10-51.895 x 10-51.918 x 10-51.941 x 10-545 1.109100750 1.09210070.027351.963 x 10-51.798 x 10-51.896 x 10-51.05910076070 1.0280.028080.72410.72280.72020.71772.008 x 10-52.052 x 10-510070.028811.995 x 10-54.158 x 10-68.036 x 10-61.252 x 10-51.356 x 10-51.465 x 10-51.578 x 10-51.696 x 10-51.818 x 10-51.880 x 10-51.944 x 10-52.009 x 10-52.074 x 10-52.141 x 10-52.208 x 10-52.277 x 10-52.346 x 10-52.416 x 10-52.487 x 10-52.632 x 10-52.780 x 10-52.931 x 10-53.086 x 10-53.243 x 10-53.565 x 10-53.898 x 10-54.241 x 10-54.593 x 10-54.954 x 10-55.890 x 10-56.871 x 10-57.892 x 10-58.951 x 10-51.004 x 10-41.117 x 10-41.352 x 10-41.598 x 10-41.855 x 10-42.122 x 10-42.398 x 10-43.908 x 10-480 0.999410080.029532.096 x 10-52.097 x 10-50.715490 0.971810082.139 x 10-52.201 x 10-510092.181 x 10-52.306 x 10-50.030240.030950.032350.033740.71320.7111100 0.9458120 0.8977140 0.85422.264 x 10-52.522 x 10-5101110130.70732.345 x 10-52.745 x 10-50.704110162.420 x 10-52.975 x 10-50.035110.036460.701410192.504 x 10-53.212 x 10-50.6992160 0.8148180 0.7788200 0.7459250 0.6746300 0.61580.037793.455 x 10-50.6974102310330.041040.0441810444.091 x 10-54.765 x 10-50.69460.6935350 0.56642.577 x 10-52.760 x 10-52.934 x 10-53.101 x 10-53.261 x 10-53.415 x 10-510560.047215.475 x 10-5400 0.524310690.69370.69480.050156.219 x 10-50.488010810.05298450500 0.45656.997 x 10-50.696510930.055723.563 x 10-57.806 x 10-50.6986600 0.404211150.060933.846 x 10-59.515 x 10-50.7037700 0.362711350.065814.111 x 10-51.133 x 10-40.7092800 0.328911530.070374.362 x 10-51.326 x 10-40.71490.300811694.600 x 10-51.529 x 10-49001000 0.27720.074650.078680.720611844.826 x 10-51.741 x 10-40.72601500 0.199012345.817 x 10-52.922 x 10-40.095990.111130.74782000 0.155312645.664 x 10-46.630 x 10-54.270 x 10-40.7539pressure P (in atm) other than 1 atm areNote: For ideal gases, the properties C, K., and Pr are independent of pressure. The properties p, v, and a at adetermined by multiplying the values of p at the given temperature by P and by dividing vand a by P.Source: Data generated from the EES software developed by S. A. Klein and F. L. Alvarado. Original sources: Keenan, Chao, Keyes, Gas Tables, Wiley, 198;and Thermophysical Properties of Matter, Vol. 3: Thermal Conductivity, Y. S. Touloukian, P. E. Liley, S. C. Saxena, Vol. 11: Viscosity, Y. S. Touloukian,S.C. Saxena, and P. Hestermans, IFI/Plenun, NY, 1970, ISBN 0-306067020-8.

Answered: Image /qna-images/answer/b78177e9-d2a3-41ad-80d8-8914405f9fed.jpg

a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow directi (Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar a a temperature of 10°C. The top surface of the wing absorbs solar radiation at a ra of 800 W/m2. Assume the wing to be of solid construction and to have a sing uniform temperature. Estimate the steady-state temperature of the wing. Refer Table A-15 for air thermophysical properties.

a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow directi (Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar a a temperature of 10°C. The top surface of the wing absorbs solar radiation at a ra of 800 W/m2. Assume the wing to be of solid construction and to have a sing uniform temperature. Estimate the steady-state temperature of the wing. Refer Table A-15 for air thermophysical properties.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Asap, in detail please
I need it urgently thank you
Consider a thin-walled, ﬁ xed-volume container of volume V that holds an ideal gas at constant temperature T. It can be shown by dimensional analysis that the number of particles striking the walls of the container per unit area per unit time is given by nv-/4, where as usual n is the particle number density. The container has a small hole of area A in its surface through which the gas can leak slowly. Assume that A is much less than the surface area of the container. (a) Assuming that the pressure inside the container is much greater than the outside pressure (so that no gas will leak from the outside back in), estimate the time it will take for the pressure inside to drop to half the initial value. Your answer should contain A, V, and the mean molecular speed v-. (b) Obtain a numerical result for a spherical container with a diameter of 40 cm containing air at 293 K, if there is a circular hole of diameter 1.0 mm in the surface.
A vertical pipe 90 mm diameter and 2.5 m height is maintained at a constant temperature of 125 o The pipe is surrounded by still atmospheric air at 25 oC. Find heat loss by natural convection. Properties of water at 75 oC: Density = 1.0145 kg/m3 Kinematic viscosity = 20.55 x10-6 m2/s Prandtl number (Pr) = 0.693 Thermal conductivity (k) = 30.06 x 10–3 W/m K
question is image only part a
This question about heat transfer/liquid. Obtain the following basic equations modeling natural convection in the two-dimensional plane at steady conditions in terms of the given dimensionless quantities. Note: The buoyancy term in the y-momentum equation will be obtained based on dimensionless numbers. Second photo gives you what you need.
Heat transfer. Show all steps for solution
Air at 10°C and 1 atm is flowing parallel at a velocity of 15.5 m/s over the top flat surface of copper plate. The top surface of the copper plate is 0.03m by 0.03m square. The temperature of copper plate is uniform at 65.6°C. For laminar flow, calculate the dimensionless Reymolds number (Nre) and Nussel number (NNu). Table A.3-3a. Physical Properties of Air at 101.325 kPa (1 Atm Abs), SI Units Bx (Bp²/1?) T (kJ/kg · u x T (Pa ·s, k (W/m 103 (1/K • (°C) T (K) (kg/m³) K) -17.8255.41.379 1.0048 1.62 × 6s or kg/m · s) · K) Npr (1/K) m³) 0.022500.7203.92 2.79 x 108 O 273.21.293 1.0048 1.72 × (0-5 0.024230.7153.65 2.04 × 108 10.0 283.21.246 1.0048 1.78 ×/0 0.024920.7133.53 1.72 x 108 37.8 311.01.137 1.0048 1.90%/0-S 0.027000.7053.22 1.12 x 108 Select one: O A. NRe = 27826.58; NNu =98.58 O B. NRe = 23215.74; NNu =152.68 O C. NRe = 27826.58; NNu = 152.68 O D. NRe = 23215.74; NNu =98.58
In the arctic sea, the ice sheets are melting. Let's calculate the temperautre distribution in one such ice sheet. The sheet is 2 m thick. Under the sheet there is ice-water mixture and it can be assumed that the temperature of the bottom surface of the ice sheet is approximately 0°C. Air at -20°C is blowing above the sheet. The convection coefficient of air is 15 W/m².K. The thermal conductivity of ice is 2.2 W/m.K. What is the temperautre of icesheet at its center (i.e., at 1 m from the surface)?
Topic: Heat transfer Completely solve and box the final answer. 1. A 20degC water flows to 50cmx60cm flat plate with velocity of 5.2m/s . The flat plate surface temperature is maintained at 40deg C. The air flows parallel to the 50cm side of the plate. If the kinematic viscosity of water is 78x10-8 m2/s, at what length the flow become turbulent?
Example of engineering application using Convection heat transfer. And draw a diagram of convection heat transfer. Note: Agricultural Machines only.
please solve it ASAP.